| Title | Fracture and Fatigue Strength Evaluation of Multiple Site Damaged Aircraft Fuselages - Curved Panel Testing and Analysis. |
|---|---|
| Record ID | 42250 |
| Personal Name Creator |
Samavedam, Gopal; Hoadley, D. |
| Source | 172p. in various pagings |
| Corporate Creator | Foster-Miller Associates; John A. Volpe National Transportation Systems Center (U.S.) |
| Publisher | United States. Department of Transportation. Federal Aviation Administration |
| Publication Date | 19940101 |
| Language | English |
| Abstract | As the fleet of commercial passenger aircraft is utilized beyond their design lives, flaws have developed at the rivet holes of fuselage lap joints on some aircraft, which can grow and link up into cracks of significant length. Understanding, predicting, and controlling this crack growth and the ensuing linkup requires analysis and evaluation of the structural parameters in concert with confirmation by testing representative models of the fuselage. A dedicated test facility has been designed, built and tested for this purpose. Seven full-sized curved fuselage panels have been built and tested. This report describes the design rationale for the facility, the details of its construction and performance and the design and testing of compatible panels which simulate fuselage structural details. Data on basic material properties of interest to the aging aircraft issue have been compiled from existing literature and from R-curve testing and rivet stiffness testing performed as part of the effort. Analytic techniques have been developed to evaluate stress distributions and to estimate elastic stress intensity factors for flat and curved test panels. A flat test panel has been designed that demonstrates hoop stress equivalence to the curved fuselage. A 3-D FE mesh of a riveted lap joint is also presented. |
| Public Note | Introduction, Selection of testing approach, Test fixture design, Test panel design and fabrication, System shakedown testing, Panel residual strength tests, Materials data, Analystic modeling, Conclusions, References, Appendices |
| Rosap ID | dot:9433 |
| Rosap URL | https://rosap.ntl.bts.gov/view/dot/9433 |
| TRT Terms | Mechanical fatigue; Fracture tests; Fuselages; Cracking; Aircraft |
| General Subjects | Fracture properties; Stresses; Aircraft; Cracking, Fatigue strength; Aging aircraft; Multiple site damage; Fuselage |
| Classification | NTL - AVIATION - Aviation Safety/Airworthiness |
| Geographical Coverage |
United States |
| OCLC | 29950519 |
| Report Number | DOT-VNTSC-FAA-93-08; DOT-FAA-CT-94-10 |
| Availability | Volpe National Transportation Systems Center, Technical Reference Center |
| Resource type | Tech Report |
| URL | https://ntlrepository.blob.core.windows.net/lib/42000/42200/42250/DOT-VNTSC-FAA-93-08.pdf |
| Format | |
| Database | NTL Digital Repository |